Preparation method of self-healing silicon-carbide-fiber-reinforced silicon-boron-nitrogen-carbon composite material

A technology of silicon-boron-nitrogen-carbon and composite materials, which is applied in the field of preparation of self-healing silicon carbide fiber-reinforced silicon-boron-nitrogen-carbon composite materials, can solve the problem of strength, toughness and reliability of thermal structural parts, ceramic matrix composite materials There are no problems such as self-healing and SiBNC fiber preparation difficulties, and achieve excellent self-healing, high-temperature mechanical properties, and low thermal expansion coefficient.

Inactive Publication Date: 2015-04-22
DONGHUA UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The disadvantage is that the prepared ceramic matrix composite material has no self-healing property. Under the action of strong alternating thermal load, the material is prone to cracks and cannot be repaired in time to break, and the service life is low.
And because SiBNC fiber is difficult to prepare, the cost is high, and it is not easy to form a prefabricated part. Using SiBNC short fiber as a reinforcing phase cannot effectively solve the problem of strength, toughness and reliability as a thermal structural part.

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0023] Prepare a 70% polysilborazane anhydrous toluene solution, transfer the prepared solution to a nitrogen-protected high-temperature tube furnace, and increase the temperature in the furnace from room temperature to 150°C at a rate of 1°C / min and keep it constant Heat 1h for crosslinking treatment. The crosslinked SiBNC ceramic precursor was ground and a 60-mesh screen to obtain SiBNC ceramic powder with a particle size of 100μm. The type of SiC preform was 2.5-dimensional woven, and the fiber volume fraction was controlled to 40%; the ground SiBNC ceramic powder The preform with SiC fiber is placed in a mold, and it is hot pressed in a hot pressing device at 200° C. for 2 hours, and then demolded after cooling to obtain a silicon carbide fiber reinforced silicon boron nitride carbon composite material. The composite material was heated to 1400°C at a rate of 1°C / min under nitrogen flow for 2 hours to crack and ceramicize, and then the ceramicized silicon carbide fiber rein...

Embodiment 2

[0025] Prepare a polysilborazane anhydrous toluene solution with a concentration of 85%, transfer the prepared solution to a high temperature tube furnace protected by nitrogen, and increase the temperature in the furnace from room temperature to 190°C at a rate of 5°C / min and keep it constant Heat for 2h for crosslinking treatment. The crosslinked SiBNC ceramic precursor is ground and a 60-mesh screen is used to obtain SiBNC ceramic powder with a particle size of 200μm. The type of SiC fiber preform is 3-dimensional weaving, and the fiber volume fraction is controlled to 45%; the ground SiBNC ceramic powder The preform with SiC fiber is placed in a mold, and it is hot-pressed in a hot-pressing device at 215°C for 2.5 hours, and then demolded after cooling to obtain a silicon carbide fiber reinforced silicon-boron-nitrogen-carbon composite material. The composite material was heated to 1500°C at a rate of 5°C / min under nitrogen flow for 3.5 hours to crack and ceramicize, and th...

Embodiment 3

[0027] Prepare a 100% polysilborazane anhydrous toluene solution, transfer the prepared solution to a high-temperature tube furnace protected by nitrogen, and increase the temperature in the furnace from room temperature to 230°C at a rate of 10°C / min and maintain a constant temperature Heat for 3h for crosslinking treatment. The crosslinked SiBNC ceramic precursor was ground and a 60-mesh screen to obtain SiBNC ceramic powder with a particle size of 300μm. The type of SiC fiber preform was 3-dimensional weaving, and the fiber volume fraction was controlled to 52%; the ground SiBNC ceramic powder The preform with SiC fiber is placed in a mold, and it is hot pressed in a hot pressing device at 230° C. for 3 hours, and then demolded after cooling to obtain a silicon carbide fiber reinforced silicon boron nitride carbon composite material. The composite material was heated to 1600°C at a rate of 10°C / min under nitrogen flow for 5 hours to crack and ceramize, and then the ceramiciz...

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Abstract

The invention relates to a preparation method of a self-healing silicon-carbide-fiber-reinforced silicon-boron-nitrogen-carbon composite material, which comprises the following steps: (1) preparing a polyborosilazane (PBSZ) precursor; dissolving the PBSZ precursor in a toluene solution under the protection of N2 to obtain a PBSZ toluene solution; transferring into a pipe furnace, crosslinking under the protection of N2, grinding and screening to obtain SiBNC precursor powder; (2) preparing SiC fibers into a prefabricated part, carrying out hot pressing on the SiBNC precursor powder and SiC fiber prefabricated part, cooling and demolding to obtain a composite material; and transferring into a pipe furnace in an N2 protective atmosphere to perform ceramization, and finally, sintering. The method is simple in technique, easy to operate and low in cost; and the prepared silicon-carbide-fiber-reinforced silicon-boron-nitrogen-carbon composite material is uniform and compact, has the advantages of favorable high-temperature stability and excellent oxidation resistance, and especially has self-healing performance.

Description

Technical field [0001] The invention belongs to the field of silicon-boron-nitrogen-carbon composite materials, and particularly relates to a preparation method of a self-healing silicon carbide fiber reinforced silicon-boron-nitrogen-carbon composite material. Background technique [0002] With the rapid progress of aerospace technology in recent years, higher requirements have been put forward for the performance of high-temperature ceramic composite materials. Among them, the effective use time of high-temperature ceramic matrix composites is an important indicator of service in aerospace high-temperature oxidation environment. The damage of a spacecraft usually starts with small cracks in its key materials. These cracks generally appear below the surface of the material, with hidden locations and small sizes that cannot be directly observed. After the cracks are formed, they will continue to grow under load, which will greatly weaken the bearing capacity of the material unti...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/80C04B35/58C04B35/622
Inventor 余木火张晨宇刘勇柯盛包
Owner DONGHUA UNIV
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